2A952 Volume 5 UREs (2016)
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- 1.(801) The control surfaces that provide the aerodynamic force to maintain attitude and directional control of the aircraft include the ailerons,
- A.
Elevator, and control wheel
- B.
Elevator, and rudder
- C.
Elevator, and flaps
- D.
Flaps, and slats
- 2.(801) Which control surfaces provide aircraft roll control?
- A.
Ailerons and flight spoilers
- B.
Ailerons and lower rudder
- C.
Flight spoilers and rudder
- D.
Ailerons and rudder
- 3.(801) For high speed aileron operation, what surfaces are used in conjunction with spoilers for roll control?
- A.
Inboard ailerons only
- B.
Inboard elevators only
- C.
Outboard ailerons only
- D.
Both inboard and outboard ailerons
- 4.(801) Snubbers protect the ailerons from wind gusts in miles per hour (mph) up to
- A.
60 mph
- B.
70 mph
- C.
80 mph
- D.
90 mph
- 5.(801) Pitch control of the aircraft about the lateral axis is accomplished by the
- A.
Elevators
- B.
Ailerons
- C.
Rudders
- D.
Spoilers
- 6.(801) Which aircraft surface provides aircraft yaw control about the vertical axis?
- A.
Elevators
- B.
Ailerons
- C.
Spoilers
- D.
Rudder
- 7.(802) What are leading-edge and trailing-edge flaps used for?
- A.
Coordinated turns
- B.
Aileron augmentation
- C.
Landings and takeoffs
- D.
Pitch and yaw maneuvers
- 8.(802) How many leading edge flap surfaces are there?
- A.
18
- B.
22
- C.
26
- D.
30
- 9.(802) The priority valve permits flow only when hydraulic pressure in pounds per square inch (psi) exceeds
- A.
2500 ±300 psi
- B.
2500 ±500 psi
- C.
2000 ±300 psi
- D.
2000 ±500 psi
- 10.(802) The flap power package receives hydraulic pressure from the number
- A.
One and number two hydraulic systems
- B.
One and number four hydraulic systems
- C.
Two and number four hydraulic systems
- D.
Two and number three hydraulic systems
- 11.(802) What provides the electrical signal used for flap asymmetry control?
- A.
Comparator units
- B.
Flap power packages
- C.
Control cables and linkages
- D.
Flap position indicating system
- 12.(803) What is not included in the mechanical flight control system?
- A.
Cables
- B.
Torque tubes
- C.
Push-pull tubes
- D.
Electrically powered actuators
- 13.(803) What is not an advantage of the use of electro-mechanical actuators?
- A.
Reduces noise
- B.
Reduces weight
- C.
Eliminates the need for hydraulic fluid
- D.
Eliminates the need for electrical power
- 14.(804) What surface trims the aircraft about the pitch axis?
- A.
Horizontal stabilizer
- B.
Gear train
- C.
Ailerons
- D.
Flaps
- 15.(804) Release of either half of the stabilizer trim control switch will
- A.
Damage the auxiliary drive
- B.
Result in nose down travel
- C.
Stop the actuator motion
- D.
Result in nose up travel
- 16.(804) The stabilizer trim autopilot servomotor supplies power to move the stabilizer during
- A.
Ground operation only
- B.
High speed operation
- C.
Low speed operation
- D.
Autopilot operation
- 17.(804) What type of action does the actuator assembly convert rotary motion into for the purpose of controlling the stabilizer trim?
- A.
Nose left or nose right motion
- B.
Vertical motion
- C.
Linear motion
- D.
Rotary speed
- 18.(805) What flight control surface indicator is designed to display percentage of surface extension?
- A.
Flap/slat position indicator
- B.
Rudder trim position indicator
- C.
Aileron trim position indicator
- D.
Horizontal stabilizer trim position indicator
- 19.(805) Synchro position indicating systems convert mechanical shaft angles to
- A.
Mechanical shaft degrees
- B.
Electrical shaft degrees
- C.
Mechanical signals
- D.
Electrical signals
- 20.(805) What type of operating power is required by a selsyn position indicating system?
- A.
26 VAC
- B.
28 VDC
- C.
115 VAC
- D.
120 VDC
- 21.(805) The selsyn position indicating system transmitter consists of a circular resistance winding with three taps positioned
- A.
45 degrees apart
- B.
90 degrees apart
- C.
120 degrees apart
- D.
180 degrees apart
- 22.(805) How accurately the selsyn position indicator rotor follows the transmitter depends upon the
- A.
Amplitude of the applied voltage
- B.
Frequency of the applied voltage
- C.
Spacing of the coils and taps
- D.
Strength of the rotor magnet
- 23.(806) Manual pitch and roll axis attitude adjustments are allowed by the
- A.
Flight control augmentation system (FCAS)
- B.
Stability augmentation system (SAS)
- C.
Flight management system (FMS)
- D.
Flight control set (FCS)
- 24.(806) The flight control set (FCS) pitch axis must be engaged for selection of altitude hold (ALT HOLD) or
- A.
Mach number hold (MACH HOLD)
- B.
Tactical air navigation (TACAN)
- C.
Navigation/localizer (NAV/LOC)
- D.
Heading select (HDG SEL)
- 25.(807) All signals needed for proper flight control set (FCS) operation are processed by the FCS
- A.
Controller
- B.
Processor
- C.
Control panel
- D.
Status/test panel
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